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in creator/contributor: "Huntley, S. C."  
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Ideal temperature rise due to constant-pressure combustion of a JP-4 fuel

Description: The ideal temperature rise due to the constant-pressure combustion of a methylene (CH sub 2) fuel was calculated. CH sub 2 fuel closely approximates MIL-F-5624 grade JP-4 fuel presently used in most turbojet and ram-jet engines. Charts are presented from which the ideal temperature rise or the ideal quantity of fuel required to obtain a specified combustion temperature may be obtained for any flight condition likely to be encountered with turbojet or ram-jet engines using this fuel. The charts … more
Date: September 27, 1955
Creator: Huntley, S. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pumping and thrust characteristics of several divergent cooling-air ejectors and comparison of performance with conical and cylindrical ejectors

Description: Report presenting an investigation of the performance of four divergent ejector configurations with shroud-exit to primary-nozzle-exit diameter ratios of 1.2 and 1.3 with minimum-shroud to primary-nozzle-exit diameter ratios of 1.1 and 1.2. A comparison of the performance of conical, cylindrical, and divergent ejectors showed that on the basis of similar design variables each configuration has merit. Results regarding the divergent-ejector performance and comparison of ejectors are provided.
Date: January 20, 1954
Creator: Huntley, S. C. & Yanowitz, Herbert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance investigation of two flame-holder and fuel-system configurations in short afterburner

Description: From Introduction: "The results of this complete evaluation of the altitude performance and operational characteristics of the two types of flame-holder and fuel-system configurations are reported herein.The starting limits of both configurations at a flight Mach number of 0.6 are also discussed."
Date: May 6, 1952
Creator: Huntley, S. C. & Wilsted, H. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers

Description: Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.
Date: July 10, 1952
Creator: Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Locked-Rotor and Windmilling Drag Characteristics of an Axial-Flow-Compressor Type Turbojet Engine

Description: The internal drag of an axial-flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8.
Date: January 17, 1952
Creator: Vincent, K. R.; Huntley, S. C. & Wilsted, H. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance investigation of a high-temperature afterburner

Description: From Introduction: "In response to the ever-increasing need for high thrust augmentation, an investigation was conducted that had as its primary objective the attainment of maximum exhaust-gas temperature and thrust (ref. 1). The investigation reported herein was therefore conducted to ascertain the operational limits of the most promising high-temperature afterburner design of reference 1 and to determine its performance over a wind range of flight conditions."
Date: June 26, 1953
Creator: Huntley, S. C.; Auble, Carmon M. & Useller, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combined compressor coolant injection and afterburning for turbojet thrust augmentation

Description: Report presenting a discussion of some of the requirements and of the application of the augmented performance of compressor coolant injection and afterburning in a turbojet engine in a high-speed, high-altitude flight. Results regarding the experimental performance of a combined system and the application of augmented performance to high-speed flight are provided.
Date: September 16, 1954
Creator: Useller, James W.; Huntley, S. C. & Fenn, David B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of inlet-air baffles on rotating-stall and stress characteristics of an axial-flow compressor in a turbojet engine

Description: Report presenting an investigation of the effect of inlet-air baffles on the rotating stall, rotor-blade vibratory stress, and performance characteristics of a compressor in an axial-flow turbojet engine. Two baffles were tested, an inside-diameter baffle extending radially outward from the hub, and an outside-diameter baffle extending radially inward from the outer casing.
Date: January 10, 1955
Creator: Huntley, S. C.; Huppert, Merle C. & Calvert, Howard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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